EP2071141B1 - Dichte Befestigung eines Lagerträgers in einem Turbotriebwerk - Google Patents

Dichte Befestigung eines Lagerträgers in einem Turbotriebwerk Download PDF

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Publication number
EP2071141B1
EP2071141B1 EP08168912A EP08168912A EP2071141B1 EP 2071141 B1 EP2071141 B1 EP 2071141B1 EP 08168912 A EP08168912 A EP 08168912A EP 08168912 A EP08168912 A EP 08168912A EP 2071141 B1 EP2071141 B1 EP 2071141B1
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EP
European Patent Office
Prior art keywords
support
cover
annular
downstream
bolts
Prior art date
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Active
Application number
EP08168912A
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English (en)
French (fr)
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EP2071141A1 (de
Inventor
Régis Eugène Henri Servant
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP2071141A1 publication Critical patent/EP2071141A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals

Definitions

  • the invention relates to a turbomachine equipped with shaft guide bearings carried by supports fixed to a casing of the turbomachine by means of fusible screws.
  • a turbofan engine comprises a fan arranged at the upstream end and driven in rotation by a shaft guided by upstream and downstream bearings carried by a first and a second annular support, respectively.
  • the upstream bearing is carried by the upstream end of the first support, whose downstream end comprises a plurality of orifices distributed over its circumference for fixing by bolting on a radially outer portion of the second support which is fixed by bolting to a housing intermediate located downstream of a low-pressure compressor.
  • the downstream end of the first support comprises an annular rim formed with a plurality of notches receiving the upstream portions of the fixing screws of the first support on the second support. These notches open into milled cavities in the rim of the support to receive the heads of the screws. Washers are engaged on the screws to form continuous bearing surfaces of the screw heads on the edge of the support.
  • the lubrication oil seal of the upstream and downstream bearings is effected by means of a first annular seal located radially outside the fixing screws in an annular groove of the upstream radial face of the second support which is in contact. with the downstream end of the first support, a second annular seal being disposed in an annular groove between two cylindrical surfaces of the second support and the intermediate casing.
  • the fastening screws used are fusible screws.
  • the unbalance generated is translated at the first support by a tensile force on the fixing screws which are able to yield when the load applied exceeds a predetermined value.
  • the attachment of these screws inside the first support leads to the ejection of the debris screws in the inter-bearing chamber, which can damage the upstream and downstream bearings and other parts located therein such that the de-oilers of the enclosure, the oil jets, etc.
  • the screws are in contact with the lubricating oil of the upstream and downstream bearings and must meet strict criteria of cleanliness.
  • the document EP 1659266A1 describes a device for decoupling two upstream and downstream bearings guiding in rotation a drive shaft of a fan arranged at the upstream end of a turbomachine.
  • the upstream bearing is connected to a first annular support fixed by fusible screws on a housing by means of an annular flange which is fixed at its radially inner end to an outer ring of the downstream bearing and carries the radially inner end of a second support whose radially outer end is fixed to the first support.
  • This flange has a U-shaped portion and ensures the rotational locking of the first and second bearing supports, the radial retention of the drive shaft and the axial retention of the fan in case of rupture of the drive shaft.
  • the present invention is intended in particular to avoid the disadvantages of the prior art in a simple, effective and economical way.
  • a turbomachine comprising a shaft guided in an upstream bearing carried by a first annular support fixed by screws to a housing by means of a second annular support carrying a downstream bearing for guiding the shaft , characterized in that the ends of the fastening screws of the first support on the second support are covered by an annular cover fixed to seal on the second support or on the housing.
  • annular cover makes it possible to cover by a single piece all the ends of the screws and to avoid, in the event of dawn loss, that debris of the screws escape inside the internal enclosure. -paliers.
  • the fastening screws of the first support are outside this support, which makes it possible to prevent solid particles present on the fusible screws from penetrating into the inter-bearing enclosure and polluting the lubricating oil of the bearings. upstream and downstream.
  • the external arrangement of the screws relative to the first support also makes it possible to maintain, in the event of blade loss, the debris of the upstream portions of the fusible screws outside the inter-bearing enclosure.
  • Fixing the downstream end of the first bearing support to the second support is carried out more simply and the use of washers is no longer necessary since the heads of the screws can be supported on their entire circumference.
  • the manufacture of the first support is also simplified since this part does not have a complex geometry at its downstream end as in the prior art.
  • the annular cover is U-section and comprises two parallel walls engaged sealingly on a cylindrical wall of the second support and inside a cylindrical wall of the housing.
  • annular seal is mounted in an annular groove of an upstream radial face of the second support or a corresponding downstream radial face of the first support and annular seals are mounted in grooves.
  • annular walls of the lid or the cylindrical walls of the second support and the cover which ensures with a small number of seals the sealing of the attachment of the first support on the second support and prevents oil from n escapes outside the inter-bearing enclosure by the screws.
  • the cover will preferably be made of a material having a coefficient of expansion similar to those of the second support and the housing.
  • Maintaining the cover in the overlap position of the ends of the screws is achieved through a cylindrical rim downstream of the lid fixed by bolts on a cylindrical rim downstream of the second support.
  • the cover can also be directly fixed by bolting on the housing.
  • the invention also relates to an annular cover for sealing the screws for fixing an upstream bearing support for guiding a shaft in a turbomachine as described above, characterized in that it has a U-section formed by two cylindrical parallel walls radially inner and radially outer respectively, of which at least the radially outer wall comprises an outer annular groove for mounting a seal.
  • the lid comprises a cylindrical rim extending in the extension of its radially inner cylindrical wall and opposite it and having regularly distributed holes through which fastening means pass.
  • the lid may be made of composite material or metal material, for example titanium.
  • FIG 1 representing an upstream part of a turbomachine according to the prior art, which comprises a blower wheel 10 driven in rotation about the axis 12 of the turbomachine by a shaft 14 whose upstream end is fixed by bolting 16 to a frustoconical wall 18
  • the shaft 14 is attached to the end of a shaft 20 of a low-pressure turbine (not shown).
  • the blower wheel 10 is secured to the rotor 22 of a low-pressure compressor associated with an intermediate casing 24.
  • the shaft 14 is supported and guided by upstream 26 and downstream 28 bearings.
  • the upstream bearing 26 is carried by the upstream end of a first annular support 30 whose downstream end is fixed by fuse screws 32 on a part radially external of a second annular support 34 carrying at its radially inner end the downstream bearing 28.
  • the second support 34 is fixed by bolts 36 on a flange 38 of the intermediate casing 24.
  • the downstream end of the first support 30 comprises notches 40 oriented radially towards the inside of the turbomachine, distributed over the entire circumference of an annular rim of the first support 30 and intended to receive the upstream end of the fuse screws 32 (FIG. figure 2 ).
  • Each notch 40 opens into a cavity 42 in which is housed the head 44 of a fuse screw 32.
  • the heads 44 of the fuse screws 32 abut the ends of the notches 40 when the nuts 48 are tightened on the fuses 32.
  • washers 46 are interposed between the heads 44 of the screws 32 and the notches 40 so as to have a continuous support of the heads 44 of the screws 32 over their entire circumference.
  • the fusible screws 32 have at their part in the notch 40 a narrowing which allows the screws 32 to break in this place when the load applied to them is too large. Indeed, in case of blade loss, the appearance of an unbalance on the fan shaft 14 is reflected at the level of the fusible screws 32 by large tensile forces.
  • the decoupling of the first 30 and second supports 34 makes it possible to accept this unbalance and to limit the transmission of forces to the intermediate casing 24 and to the whole of the turbomachine.
  • the first support 50 comprises a frustoconical wall 56 of upstream reducing section which carries at its upstream end the upstream bearing 26 and is connected at its downstream end to a cylindrical wall 58 whose downstream end comprises an annular rim 60 s extending radially outward. Screw holes are formed in the annular flange 60 and are aligned with corresponding holes in the radially outer portion of the second support 52 to receive the fusible screws 32.
  • the upstream end of each fusible screw 32 comprises a head 44 axial support over its entire circumference on the upstream face of the annular flange 60, its downstream end receiving a nut 62 clamped on the radially outer portion of the second support 52.
  • annular cover 54 which has a U-shaped transverse section and comprises two parallel walls, radially inner 64 and outer 66, respectively, the inner wall 64 being connected to a cylindrical rim 68 extending downstream and having screw holes regularly distributed around the axis 12 of the turbomachine.
  • the cover 54 covers the downstream end of the fuse screws 32 and its radially inner 64 and outer 66 walls are sealingly engaged on a cylindrical wall 70 of the second support 52 and in a cylindrical wall 72 of the flange 38 of the intermediate housing 24.
  • the cover 54 is held in position by screws 73 inserted into the orifices of the downstream cylindrical rim 68 of the cover 54 and into corresponding orifices of a cylindrical rim 74 of the second support 52.
  • the radially outer wall 66 of the cover 54 and the cylindrical wall 70 of the second support 52 each comprise an annular groove oriented radially outwards and receiving an annular seal 76, 78. These two annular seals 76, 78 prevent the the lubricating oil of the upstream 26 and downstream 28 bearings does not escape through the passage openings of the fusible screws 32 and at the contact zones. between the second support 52 and the intermediate housing 24.
  • a third annular seal 80 is mounted in an annular groove of an upstream radial face of the second support 52, this upstream face being in contact with a radial downstream face of the first support 50.
  • This seal 80 is located radially inside the screws. fuses 32 to prevent oil leakage through the screw holes formed in the flange 60.
  • the annular cover 54 makes it possible to contain the debris of the downstream ends of the fuse screws 32, whereas the fixing of the screws 32 radially outside the first support 50 makes it possible to avoid that the debris of the heads 44 of the screws 32 penetrate the inter-bearing chamber and damage the parts located therein.
  • the cover 54 also makes it possible to seal the downstream end of the fusible screws 32 and to simplify the manufacture of the first support 50 since it is no longer necessary to make notches and cavities in a rim of this support.
  • the radially outer end of the second support 52 is fixed to the intermediate casing 24 by means of bolts 36, screwed into a flange 38 of the intermediate casing 24.
  • the cover 54 is made of a material having a coefficient of thermal expansion close to that of the materials of the second support 52 and the intermediate casing 24, in order to guarantee perfect sealing by the annular seals 76, 78, 80 at the temperatures at which they are submitted these different parts.
  • the cover 54 may be made of composite material or metal material, such as titanium for example.
  • the lid 54 may comprise a downstream radial annular flange fixed by bolts on an annular flange downstream of the second support 52 or the flange 38 of the intermediate casing 24.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Claims (12)

  1. Turbomaschine mit einer Welle (14), die in einem vorgeschalteten Lager (26) geführt ist, das von einem ersten ringförmigen Träger (50) getragen ist, der durch Schrauben (32) über einen ein nachgeschaltetes Lager (28) zum Führen der Welle (14) tragenden zweiten ringförmigen Träger (52) an einem Gehäuse (24) befestigt ist, dadurch gekennzeichnet, dass die Enden der Schrauben zur Befestigung (32) des ersten Trägers an dem zweiten Träger mit einem ringförmigen Deckel (54) abgedeckt sind, der an dem zweiten Träger (52) oder an dem Gehäuse (24) dicht befestigt ist.
  2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, dass die Befestigungsschrauben (32) des ersten Trägers (50) außerhalb dieses Trägers (50) gelegen sind.
  3. Turbomaschine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Deckel (54) einen U-förmigen Querschnitt aufweist und zwei parallele Wände umfasst, die an einer zylindrischen Wand (70) des zweiten Trägers (52) dicht angreifen und in eine zylindrische Wand (72) des Gehäuses (24) dicht eingreifen.
  4. Turbomaschine nach Anspruch 3, dadurch gekennzeichnet, dass Ringdichtungen (76, 78, 80) in ringförmigen Nuten der Wände (64, 66) des Deckels (54) oder der zylindrischen Wände des zweiten Trägers (52) und des Deckels (54) angebracht sind.
  5. Turbomaschine nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Enden der Schrauben (32), die innerhalb des Deckels gelegen sind, Muttern (62) tragen.
  6. Turbomaschine nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass eine Ringdichtung (80) in einer ringförmigen Nut einer vorgeordneten Radialfläche des zweiten Trägers oder einer entsprechenden
    nachgeordneten Radialfläche des ersten Trägers (50) angebracht ist.
  7. Turbomaschine nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Deckel (54) aus einem Werkstoff gefertigt ist, der einen ähnlichen Ausdehnungskoeffizienten wie der zweite Träger (52) und das Gehäuse (24) aufweist.
  8. Turbomaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der Deckel (54) einen nachgeordneten zylindrischen Rand (68) aufweist, der durch Bolzen (73) an einem nachgeordneten zylindrischen Rand (74) des zweiten Trägers (52) befestigt ist.
  9. Turbomaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der Deckel (54) durch Bolzen an dem Gehäuse (24) befestigt ist.
  10. Ringförmiger Deckel zum dichten Abdecken der Befestigungsschrauben eines Trägers eines vorgeschalteten Lagers zum Führen einer Welle in einer Turbomaschine nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass er einen U-förmigen Querschnitt aufweist, der von zwei zylindrischen parallelen Wänden, einer radial inneren (64) bzw. einer radial äußeren (66), gebildet ist, von denen wenigstens die radial äußere Wand (66) eine ringförmige äußere Nut zum Anbringen einer Dichtung (78) aufweist.
  11. Deckel (54) nach Anspruch 10, dadurch gekennzeichnet, dass er aus Verbundwerkstoff oder aus metallischem Werkstoff, wie zum Beispiel Titan gefertigt ist.
  12. Deckel nach Anspruch 10 oder 11, dadurch gekennzeichnet, dass er einen zylindrischen Rand (68) aufweist, der sich in der Verlängerung seiner radial inneren zylindrischen Wand (64) und entgegengesetzt zu dieser erstreckt und gleichmäßig verteilte Öffnungen für den Durchgang von Befestigungsmitteln aufweist.
EP08168912A 2007-12-14 2008-11-12 Dichte Befestigung eines Lagerträgers in einem Turbotriebwerk Active EP2071141B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708706A FR2925123A1 (fr) 2007-12-14 2007-12-14 Etancheite de fixation de support de palier dans une turbomachine

Publications (2)

Publication Number Publication Date
EP2071141A1 EP2071141A1 (de) 2009-06-17
EP2071141B1 true EP2071141B1 (de) 2011-06-22

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US (1) US20090155073A1 (de)
EP (1) EP2071141B1 (de)
JP (1) JP2009144715A (de)
CA (1) CA2646976A1 (de)
FR (1) FR2925123A1 (de)
RU (1) RU2008149140A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2025242991A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242993A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242992A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242994A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
FR3162463A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162464A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162462A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef

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US8573922B2 (en) 2010-06-15 2013-11-05 Rolls-Royce Corporation Bearing support
US9309775B2 (en) * 2012-05-21 2016-04-12 United Technologies Corporation Rotational debris discourager for gas turbine engine bearing
US9488110B2 (en) * 2013-03-08 2016-11-08 General Electric Company Device and method for preventing leakage of air between multiple turbine components
EP2873810B2 (de) 2013-11-18 2020-07-01 Safran Aero Boosters SA Ringförmiger Deckel zur Begrenzung der Lagerkammer eines Turbotriebwerks
US10247106B2 (en) * 2016-06-15 2019-04-02 General Electric Company Method and system for rotating air seal with integral flexible heat shield
CN107121289B (zh) * 2017-04-21 2019-04-23 中国航发沈阳发动机研究所 一种航空发动机高增压比风扇试验件的轴承腔封严系统
JP7032279B2 (ja) * 2018-10-04 2022-03-08 本田技研工業株式会社 ガスタービンエンジン

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FR2624913B1 (fr) * 1987-12-16 1990-04-20 Snecma Dispositif de fixation a vis d'une piece de revolution sur une bride annulaire de turbomachine
US6240719B1 (en) * 1998-12-09 2001-06-05 General Electric Company Fan decoupler system for a gas turbine engine
EP1314854A1 (de) * 2001-11-23 2003-05-28 Techspace Aero S.A. Entkopplungseinrichtung für einen Luftfahrzeugsmotor
FR2845126B1 (fr) * 2002-09-26 2004-12-03 Snecma Moteurs Dispositif decoupleur en traction
FR2866068B1 (fr) * 2004-02-06 2006-07-07 Snecma Moteurs Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers
FR2866069A1 (fr) * 2004-02-06 2005-08-12 Snecma Moteurs Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers
FR2871517B1 (fr) * 2004-06-11 2006-09-01 Snecma Moteurs Sa Turbomachine avec moyens de retenue axiale du rotor
FR2878289A1 (fr) * 2004-11-19 2006-05-26 Snecma Moteurs Sa Turbomachine avec un dispositif de decouplage commun aux premier et deuxieme paliers de son arbre d'entrainement
FR2901315B1 (fr) * 2006-05-19 2010-09-10 Hispano Suiza Sa Boitier d'accessoires dans un moteur d'avion tel qu'un turboreacteur

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2025242991A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242993A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242992A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
WO2025242994A1 (fr) 2024-05-24 2025-11-27 Safran Aircraft Engines Module pour une turbomachine d'aéronef avec circuit d'alimentation en huile de l'enceinte de lubrification
FR3162460A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162467A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162461A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162463A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162464A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162468A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef
FR3162462A1 (fr) * 2024-05-24 2025-11-28 Safran Aircraft Engines Module pour une turbomachine d’aeronef

Also Published As

Publication number Publication date
FR2925123A1 (fr) 2009-06-19
CA2646976A1 (fr) 2009-06-14
JP2009144715A (ja) 2009-07-02
US20090155073A1 (en) 2009-06-18
EP2071141A1 (de) 2009-06-17
RU2008149140A (ru) 2010-06-20

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